Future NASA Earth Observing System (EOS) Spacecraft will make measurements of the earth's clouds, oceans, atmosphere, land and radiation balance. These EOS Spacecraft will be part of the NASA Mission to Planet Earth. This paper specifically addresses the EOS AM Spacecraft, referred to as 'AM' because it has a sun-synchronous orbit with a 10:30 AM descending node. This paper describes the EOS AM Spacecraft mission orbit requirements, orbit determination, orbit control, and navigation system impact on earth based pointing. The EOS AM Spacecraft will be the first spacecraft to use the TDRSS Onboard Navigation System (TONS) as the primary means of navigation. TONS flight software will process one-way forward Doppler measurements taken during scheduled TDRSS contacts. An extended Kalman filter will estimate spacecraft position, velocity, drag coefficient correction, and ultrastable master oscillator frequency bias and drift. The TONS baseline algorithms, software, and hardware implementation are described in this paper. TONS integration into the EOS AM Spacecraft Guidance, Navigation, and Control (GN&C) System; TONS assisted onboard time maintenance; and the TONS Ground Support System (TGSS) are also addressed.
Orbit Determination and Orbit Control for the Earth Observing System (EOS) AM Spacecraft
1993
18 pages
Report
Keine Angabe
Englisch
Astronautics , Spacecraft Trajectories & Flight Mechanics , Unmanned Spacecraft , Navigation Systems , Earth observing system (EOS) , Flight control , Navigation aids , Orbit calculation , Satellite attitude control , Satellite orbits , Tdr satellites , Airborne/spaceborne computers , Applications programs (Computers) , Kalman filters , Onboard equipment , Aerodynamic coefficients , Aerodynamic drag , Algorithms , Atmospheric radiation , Computer programs , Earth atmosphere , Energy budgets , Ground support systems , Guidance (Motion) , Mission planning , Spacecraft guidance